Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring

Stephen P. Lynch, Karen A. Thole, Atul Kohli, Christopher Lehane

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

Three-dimensional contouring of the compressor and turbine endwalls in a gas turbine engine has been shown to be an effective method of reducing aerodynamic losses by mitigating the strength of the complex vortical structures generated at the endwall. Reductions in endwall heat transfer in the turbine have been also previously measured and reported in the literature. In this study, computational fluid dynamics simulations of a turbine blade with and without nonaxisymmetric endwall contouring were compared to experimental measurements of the exit flowfield, endwall heat transfer and endwall film-cooling. Secondary kinetic energy at the cascade exit was closely predicted with a simulation using the SST k-ω turbulence model. Endwall heat transfer was overpredicted in the passage for both the SST k-ω and realizable k-ε turbulence models, but heat transfer augmentation for a non-axisymmetric contour relative to a flat endwall showed fair agreement to the experiment. Measured and predicted film-cooling results indicated that the nonaxisymmetric contouring limits the spread of film-cooling flow over the endwall depending upon the interaction of the film with the contour geometry.

Original languageEnglish (US)
Title of host publicationASME Turbo Expo 2010
Subtitle of host publicationPower for Land, Sea, and Air, GT 2010
Pages1641-1653
Number of pages13
EditionPARTS A AND B
DOIs
StatePublished - Dec 1 2010
EventASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010 - Glasgow, United Kingdom
Duration: Jun 14 2010Jun 18 2010

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume4

Other

OtherASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010
CountryUnited Kingdom
CityGlasgow
Period6/14/106/18/10

Fingerprint

Turbomachine blades
Turbines
Heat transfer
Cooling
Turbulence models
Kinetic energy
Gas turbines
Compressors
Aerodynamics
Computational fluid dynamics
Geometry
Computer simulation
Experiments

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Lynch, S. P., Thole, K. A., Kohli, A., & Lehane, C. (2010). Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring. In ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010 (PARTS A AND B ed., pp. 1641-1653). (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B). https://doi.org/10.1115/GT2010-22984
Lynch, Stephen P. ; Thole, Karen A. ; Kohli, Atul ; Lehane, Christopher. / Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring. ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B. ed. 2010. pp. 1641-1653 (Proceedings of the ASME Turbo Expo; PARTS A AND B).
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Lynch, SP, Thole, KA, Kohli, A & Lehane, C 2010, Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring. in ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B edn, Proceedings of the ASME Turbo Expo, no. PARTS A AND B, vol. 4, pp. 1641-1653, ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010, Glasgow, United Kingdom, 6/14/10. https://doi.org/10.1115/GT2010-22984

Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring. / Lynch, Stephen P.; Thole, Karen A.; Kohli, Atul; Lehane, Christopher.

ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B. ed. 2010. p. 1641-1653 (Proceedings of the ASME Turbo Expo; Vol. 4, No. PARTS A AND B).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Lynch SP, Thole KA, Kohli A, Lehane C. Computational predictions of heat transfer and film-cooling for a turbine blade with non-axisymmetric endwall contouring. In ASME Turbo Expo 2010: Power for Land, Sea, and Air, GT 2010. PARTS A AND B ed. 2010. p. 1641-1653. (Proceedings of the ASME Turbo Expo; PARTS A AND B). https://doi.org/10.1115/GT2010-22984